Global patent index - EP 1092626 A2

EP 1092626 A2 2001-04-18 - Solar wing thermal shock compensation using solar wing position actuator

Title (en)

Solar wing thermal shock compensation using solar wing position actuator

Title (de)

Ausgleich eines Thermalschocks auf einem Solarflügel bei Anwendung seines Stellantriebes

Title (fr)

Compensation d'un choc thermique affectant un panneau solaire par l'actuateur de position du panneau

Publication

EP 1092626 A2 (EN)

Application

EP 00121358 A

Priority

US 41615799 A

Abstract (en)

A method, apparatus, article of manufacture for compensating for solar wing thermal shock in a spacecraft (100) is disclosed. The method comprises the steps of determining solar wing compensation to compensate for the thermal shock disturbance and rotating the solar wing (114) about a second axis (110) according to the determined compensation, wherein the second axis (110) is substantially perpendicular to a first axis (118) and to a vector (204) from the spacecraft (100) to the sun. The solar wing compensation can be based on predicted solar wing (114) deflections due to thermal shock perturbations, or if available, solar wing temperature measurements. In an embodiment of the present invention applicable to satellites with multiple solar wings (114), asymmetric control is applied by independent adjustment of the thermal shock compensation loop (302) controlling each solar wing (114). In yet another embodiment of the present invention, the solar wing position actuator (108) is further commanded by a feedback control loop (330) using the measured spacecraft attitude. The apparatus comprises an attitude control system having a device (310) for predicting or measuring solar wing perturbations, at least one solar wing position actuator (108), cooperatively coupled to the solar wing (114) for rotating the solar wing (114) about a second axis (110), wherein the second axis (110) is substantially perpendicular to the first axis (108) and to a vector (204) from the spacecraft (100) to the sun, and a thermal shock compensation loop (302), for generating at least one solar wing position actuator command (316) to rotate the solar wing (114) about the second axis (110) in accordance with the predicted or measured solar wing perturbations. <IMAGE>

IPC 1-7 (main, further and additional classification)

B64G 1/44; B64G 1/24

IPC 8 full level (invention and additional information)

B64G 1/24 (2006.01); B64G 1/38 (2006.01); B64G 1/40 (2006.01); B64G 1/44 (2006.01); B64G 1/28 (2006.01); B64G 1/36 (2006.01)

CPC (invention and additional information)

B64G 1/407 (2013.01); B64G 1/24 (2013.01); B64G 1/38 (2013.01); B64G 1/443 (2013.01); B64G 1/283 (2013.01); B64G 1/288 (2013.01); B64G 1/361 (2013.01); B64G 1/363 (2013.01); B64G 1/366 (2013.01)

Citation (applicant)

Designated contracting state (EPC)

DE FR GB IT

EPO simple patent family

EP 1092626 A2 20010418; EP 1092626 A3 20020925; EP 1092626 B1 20050803; EP 1092626 B9 20060628; EP 1092626 B9 20070502; CA 2323030 A1 20010411; CA 2323030 C 20040518; DE 60021674 D1 20050908; DE 60021674 T2 20060608; US 6318675 B1 20011120

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